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The following is an aerostructural shape optimization case for the MACH tutorial wing in subsonic conditions.

Case: Wing aerostructural optimization 
Geometry: MACH tutorial wing
Objective function: Drag coefficient (CD)
Lift coefficient (CL): 0.5
Design variables: 96 FFD points moving in the y direction, seven twists, and one angle of attack.
Constraints: volume, thickness, LE/TE, lift, and stress constraints (total number: 118)
Mach number: ~0.3 (100 m/s)
Reynolds number: ~30 million
Mesh cells: ~38,000
Solver: DARhoSimpleFoam

Fig. 1. Mesh and FFD points for the MACH tutorial wing.

To run this case, first download tutorials and untar it. Then go to tutorials-main/MACH_Tutorial_Wing and run the “preProcessing.sh” script to generate the mesh:


The above script will generate a structured hex mesh using pyHyp. Then, use the following command to run the optimization with 8 CPU cores:

mpirun -np 8 python runScript_AeroStruct.py 2>&1 | tee logOpt.txt